Buckling analysis of the SSCC composite sandwich cylindrical panel under axial compression

Analytical solution of the buckling problem for a composite cylindrical sandwich panel subjected to axial load is presented in the paper. The straight longitudinal edges of the panel are fully clamped, and the curved sides are simply supported. This loading results in the biaxial compression of the panel. The buckling analysis is performed using the equations of the engineering theory of laminated cylindrical shells, taking into account the transverse shear deformations. The system of linearized buckling equations is derived in terms of unknown displacements, deflection, and angles of rotation of the normal to the middle surface of the panel. The equations are solved by combining the Levy and Galerkin methods. In this approach, the deformed panel was approximated by trigonometry and beam functions. The analytical formula for the critical load has been derived and verified using finite-element analysis. Based on this formula, the influence of Poisson's effect on the value of buckling load has been studied. Design application of the formula is demonstrated for a specified value of the critical load.

Automated summary

This paper presents an analytical solution for the buckling problem of a composite cylindrical sandwich panel subjected to axial load. The study considers different boundary conditions and loading scenarios, utilizing engineering theory equations and numerical methods to derive a critical load formula. The formula is verified through finite-element analysis and demonstrates the influence of Poisson's effect on the buckling load value.